FR3128492A1 - AUXILIARY POWER UNIT WITH INTEGRATED CHARGE COMPRESSOR - Google Patents
AUXILIARY POWER UNIT WITH INTEGRATED CHARGE COMPRESSOR Download PDFInfo
- Publication number
- FR3128492A1 FR3128492A1 FR2111404A FR2111404A FR3128492A1 FR 3128492 A1 FR3128492 A1 FR 3128492A1 FR 2111404 A FR2111404 A FR 2111404A FR 2111404 A FR2111404 A FR 2111404A FR 3128492 A1 FR3128492 A1 FR 3128492A1
- Authority
- FR
- France
- Prior art keywords
- power unit
- auxiliary power
- aircraft
- compressor
- air
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas- turbine plants for special use
- F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
- F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
- F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/321—Application in turbines in gas turbines for a special turbine stage
- F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
- F05D2220/3218—Application in turbines in gas turbines for a special turbine stage for a special compressor stage for an intermediate stage of a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/50—Application for auxiliary power units (APU's)
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/51—Inlet
Abstract
Ce groupe auxiliaire de puissance pour un aéronef (1) muni d’un compresseur centrifuge à deux étages, ayant un port de prélèvement (7) pour la fourniture d’air sous pression à un système d’air de l’aéronef est situé entre l’étage amont (2) et l’étage aval (3), ce dernier étant muni à son entrée d’une grille de pré-rotation à calage variable. Figure pour l’abrégé : [Fig 3]This auxiliary power unit for an aircraft (1) provided with a two-stage centrifugal compressor, having a bleed port (7) for the supply of pressurized air to an air system of the aircraft is located between the upstream stage (2) and the downstream stage (3), the latter being provided at its input with a variable-pitch pre-rotation gate. Figure for abstract: [Fig 3]
Description
La présente invention concerne les groupes auxiliaires de puissance (APU) pour un aéronef permettant de combler les besoins en fourniture d’air de l’aéronef essentiellement lorsqu’il est au sol, lorsque les moteurs principaux sont à l’arrêt ou pour démarrer un moteur principal équipé d’un démarreur pneumatique. En vol avec les moteurs principaux en fonctionnement, il peut y avoir également un besoin de prélever de l’air pour l’habitacle sur le compresseur de charge de l’APU, par exemple en cas de problème sur le prélèvement d’air des moteurs principaux de l’avion, ou en haute altitude.The present invention relates to auxiliary power units (APU) for an aircraft making it possible to meet the air supply needs of the aircraft essentially when it is on the ground, when the main engines are stopped or to start a main engine equipped with a pneumatic starter. In flight with the main engines operating, there may also be a need to bleed air for the cockpit from the APU charge compressor, for example in the event of a problem with the bleed air from the engines main planes, or at high altitude.
L’APU peut également fournir un supplément d’énergie électrique à l’aéronef, par exemple afin de compenser une diminution momentanée du prélèvement de puissance mécanique des génératrices électriques implantées sur les moteurs principaux. Également en cas de panne d’un moteur principal, l’APU est activé pour remplacer la génératrice du moteur en panne. Cette capacité est obligatoire pour les vols ETOPS (Extended-range Twin-engine Operation Performance Standards) et rend donc la disponibilité de l’APU indispensable pour ceux-ci, ajoutant des contraintes supplémentaires de certification de l’APU.The APU can also provide additional electrical power to the aircraft, for example to compensate for a temporary reduction in the mechanical power drawn from the electrical generators installed on the main engines. Also in the event of a main engine failure, the APU is activated to replace the generator of the failed engine. This capability is mandatory for ETOPS (Extended-range Twin-engine Operation Performance Standards) flights and therefore makes the availability of the APU essential for them, adding additional APU certification constraints.
La présente invention vise à constituer un groupe auxiliaire de puissance qui est particulièrement efficient.The present invention aims to constitute an auxiliary power unit which is particularly efficient.
Techniques antérieuresPrior techniques
On connaît des APU pour aéronefs qui permettent de lui fournir un apport d’air. Deux types d’APU sont actuellement utilisés : les APU à prélèvement dans lesquels l’air fourni à l’aéronef est prélevé en sortie du compresseur de la turbomachine, et les APU à compresseur de charge dans lesquels l’air fourni est produit par un compresseur dédié, appelé compresseur de charge.APUs for aircraft are known which make it possible to provide it with an air supply. Two types of APU are currently used: bleed APUs in which the air supplied to the aircraft is taken from the turbomachine compressor outlet, and charge compressor APUs in which the supplied air is produced by a dedicated compressor, called load compressor.
Les APU à prélèvement sont peu performants en termes de rendement énergétique et d’encombrement à cause de la limitation du rapport de pression du compresseur à une valeur dictée par le niveau de pression requis par l’aéronef, de l’ordre de trois à quatre bars.Bleeding APUs perform poorly in terms of fuel efficiency and size due to the limitation of the compressor pressure ratio to a value dictated by the level of pressure required by the aircraft, of the order of three to four bars.
Le rapport de pression du cycle thermodynamique s’en trouve alors limité à environ quatre.The pressure ratio of the thermodynamic cycle is then limited to about four.
Cette configuration est donc traditionnellement réservée essentiellement aux petites machines (avions d’affaires, chasseurs).This configuration is therefore traditionally reserved mainly for small machines (business jets, fighters).
Dans les APU à compresseur de charge, celui-ci est entraîné par la turbomachine dédiée dont le rapport de pression n’est alors plus limité par le niveau requis de pression de l’air fourni à l’aéronef.In charge compressor APUs, the latter is driven by the dedicated turbomachine whose pressure ratio is then no longer limited by the required level of air pressure supplied to the aircraft.
Néanmoins, pour limiter le nombre total de composants et donc la masse, le coût et l’encombrement de l’APU, on utilise un compresseur centrifuge dont le taux de pression est limité typiquement aux alentours de huit.Nevertheless, to limit the total number of components and therefore the mass, cost and size of the APU, a centrifugal compressor is used whose pressure rate is typically limited to around eight.
De plus, lorsqu’on n’a pas de demande d’air pour l’aéronef, il est nécessaire de conserver un débit minimum dans le compresseur de charge pour le refroidir afin d’éviter des dommages irréversibles (fusion par exemple), ce qui conduit à une puissance résiduelle absorbée typiquement de l’ordre de six pourcents de la puissance totale.In addition, when there is no air demand for the aircraft, it is necessary to maintain a minimum flow rate in the load compressor to cool it in order to avoid irreversible damage (melting for example), which which leads to a residual power absorbed typically of the order of six percent of the total power.
D’autre part, le compresseur de charge nécessite généralement une entrée d’air double rallongeant la machine et conduisant souvent à l’implantation d’un palier entre les deux compresseurs pour des raisons de stabilité dynamique de la ligne d’arbre.On the other hand, the load compressor generally requires a double air inlet, lengthening the machine and often leading to the installation of a bearing between the two compressors for reasons of dynamic stability of the shaft line.
L’invention a pour but de pallier au moins certains des inconvénients précités et de proposer un groupe auxiliaire de puissance pour aéronef capable de cumuler des avantages de puissance, de compacité et d’efficience pour sa mise en œuvre, et ce sur une grande plage de fonctionnement en débit.The object of the invention is to overcome at least some of the aforementioned drawbacks and to propose an auxiliary power unit for an aircraft capable of combining the advantages of power, compactness and efficiency for its implementation, and this over a wide range. flow rate operation.
Au vu de ce qui précède, l’invention a pour objet un groupe auxiliaire de puissance muni d’un compresseur centrifuge à deux étages, ayant un port de prélèvement pour la fourniture d’air sous pression à un système d’air de l’aéronef situé entre l’étage amont et l’étage aval, ce dernier étant muni à son entrée d’une grille de pré-rotation à calage variable.In view of the foregoing, the subject of the invention is an auxiliary power unit provided with a two-stage centrifugal compressor, having a bleed port for the supply of pressurized air to an air system of the aircraft located between the upstream stage and the downstream stage, the latter being fitted at its inlet with a pre-rotation grid with variable pitch.
De préférence, l’étage aval comporte un compresseur centrifuge haute pression et l’étage amont comporte un compresseur de charge basse pression monté coaxialement en série avec le compresseur haute pression.Preferably, the downstream stage comprises a high pressure centrifugal compressor and the upstream stage comprises a low pressure load compressor mounted coaxially in series with the high pressure compressor.
De plus, l’étage amont peut comporter également un compresseur de charge basse pression monté coaxialement en série avec le compresseur haute pression.In addition, the upstream stage can also include a low pressure charge compressor mounted coaxially in series with the high pressure compressor.
Avantageusement, l’étage amont est également muni à son entrée d’une grille de pré-rotation à calage variable.Advantageously, the upstream stage is also provided at its input with a variable-pitch pre-rotation gate.
Selon une forme de réalisation, le compresseur de charge basse pression est centrifuge et comporte un couvercle dans lequel est réalisé un prélèvement d’air pour améliorer la stabilité du compresseur.According to one embodiment, the low-pressure charge compressor is centrifugal and comprises a cover in which an air bleed is made to improve the stability of the compressor.
Dans un mode de réalisation, le couvercle est formé par un carter statorique qui entoure des aubes d’un rotor du compresseur de charge basse pression.In one embodiment, the cover is formed by a stator casing which surrounds blades of a rotor of the low pressure load compressor.
Avantageusement, le port de prélèvement comporte, sur un port déjà prévu pour les besoins de l’aéronef, une dérivation vers une vanne de décharge dédiée à la régulation du compresseur de charge basse pression.Advantageously, the sampling port comprises, on a port already provided for the needs of the aircraft, a diversion to a relief valve dedicated to the regulation of the low pressure charge compressor.
De préférence, l’étage amont comporte un rouet permettant une diffusion radiale de l’air et la grille de pré-rotation à calage variable se situe axialement en aval dudit rouet.Preferably, the upstream stage comprises an impeller allowing radial diffusion of the air and the variable-pitch pre-rotation grid is located axially downstream of said impeller.
L'invention concerne également un groupe auxiliaire de puissance dans lequel la grille de pré-rotation à calage variable de l’étage aval est calée selon un angle de sensiblement moins cinq degrés d’angle par rapport à la verticale en l’absence de prélèvement d’air pour l’aéronef, et selon un angle de sensiblement quarante-cinq degrés d’angle par rapport à la verticale lors de prélèvement d’air pour l’aéronef.The invention also relates to an auxiliary power unit in which the variable-pitch pre-rotation grid of the downstream stage is pitched at an angle of substantially less than five degrees of angle relative to the vertical in the absence of tapping of air for the aircraft, and at an angle of substantially forty-five degrees of angle relative to the vertical when taking in air for the aircraft.
Il peut également être prévu que la grille de pré-rotation à calage variable de l’étage amont soit calée selon un angle de sensiblement quarante degrés d’angle par rapport à la verticale en l’absence de prélèvement d’air pour l’aéronef, et selon un angle de zéro à cinquante degrés d’angle par rapport à la verticale lors de prélèvement d’air pour l’aéronef.Provision may also be made for the variable-pitch pre-rotation grid of the upstream stage to be pitched at an angle of substantially forty degrees relative to the vertical in the absence of air bleed for the aircraft , and at an angle of zero to fifty degrees from the vertical when bleed air for the aircraft.
L'invention sera mieux comprise à l'étude détaillée des dessins annexés, sur lesquels :The invention will be better understood on detailed study of the accompanying drawings, in which:
Claims (9)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR2111404A FR3128492A1 (en) | 2021-10-27 | 2021-10-27 | AUXILIARY POWER UNIT WITH INTEGRATED CHARGE COMPRESSOR |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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FR2111404 | 2021-10-27 | ||
FR2111404A FR3128492A1 (en) | 2021-10-27 | 2021-10-27 | AUXILIARY POWER UNIT WITH INTEGRATED CHARGE COMPRESSOR |
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FR3128492A1 true FR3128492A1 (en) | 2023-04-28 |
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FR2111404A Pending FR3128492A1 (en) | 2021-10-27 | 2021-10-27 | AUXILIARY POWER UNIT WITH INTEGRATED CHARGE COMPRESSOR |
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Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20230182919A1 (en) * | 2017-06-30 | 2023-06-15 | General Electric Company | Propulsion system for an aircraft |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3680309A (en) * | 1969-09-25 | 1972-08-01 | Garrett Corp | Two-spool auxiliary power unit and control means |
GB2100361A (en) * | 1981-06-15 | 1982-12-22 | Garrett Corp | Apparatus for attenuating vortex whistle noise |
US20040006994A1 (en) * | 2002-05-16 | 2004-01-15 | Walsh Philip P. | Gas turbine engine |
FR2966529A1 (en) | 2010-10-21 | 2012-04-27 | Turbomeca | TURBOMACHINE CENTRIFUGAL COMPRESSOR COVER COVER ATTACHMENT METHOD, COMPRESSOR COVER OF IMPLEMENTATION AND COMPRESSOR ASSEMBLY PROVIDED WITH SUCH COVER |
-
2021
- 2021-10-27 FR FR2111404A patent/FR3128492A1/en active Pending
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3680309A (en) * | 1969-09-25 | 1972-08-01 | Garrett Corp | Two-spool auxiliary power unit and control means |
GB2100361A (en) * | 1981-06-15 | 1982-12-22 | Garrett Corp | Apparatus for attenuating vortex whistle noise |
US20040006994A1 (en) * | 2002-05-16 | 2004-01-15 | Walsh Philip P. | Gas turbine engine |
FR2966529A1 (en) | 2010-10-21 | 2012-04-27 | Turbomeca | TURBOMACHINE CENTRIFUGAL COMPRESSOR COVER COVER ATTACHMENT METHOD, COMPRESSOR COVER OF IMPLEMENTATION AND COMPRESSOR ASSEMBLY PROVIDED WITH SUCH COVER |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20230182919A1 (en) * | 2017-06-30 | 2023-06-15 | General Electric Company | Propulsion system for an aircraft |
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